The performance of various passive and active vibration control devices for equipment aboard spacecraft is analyzed. Several vibration control mechanisms, including pure friction, spring- damper, resilient friction and active friction control systems, are studied. Peak responses of equipment and their light subsystems under spacecraft g-jitter excitation are evaluated, and the results are compared to those for a payload with a fixed-base (rigidly attached) condition. For the frictional vibration control mechanisms, the nonlinear Coulomb model is used in the numerical simulation and the stick/slip condition at each time step is carefully evaluated. A tentative design for a new active friction control mechanism, by varying the normal force, is described. The device uses a velocity feedback to control the normal interface force with the aid of a magnet. By eliminating and/or minimizing the stick duration, the overall payload response reduces. Sensitivity of the performance of various vibration isolation mechanisms, to variations in the isolator properties, spacecraft excitation amplitude and equipment and subsystem frequency is also analyzed. The results show that the passive and active vibration control devices considered are generally highly effective in controlling the g-jitter vibration. In addition, these vibration control systems are insensitive to small deviations from their design conditions.